RU2569658C2 - Space platform - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: space platform comprises module of service systems shaped to parallelepiped, assemblies of coupling with separation system, engine unit, solar cells and thermal control system. Space platform comprises cylindrical compartment composed of grate-like structure of black-reinforced plastic and cellular cells with supports. Said cylindrical compartment houses the tanks with working fluid for engine unit of correction system with plasma engine running on xenon and engine units of orientation and stabilisation system.

EFFECT: compact design, accelerated production of spacecraft based on this platform.

4 dwg, 4 cl

Description

The present invention is intended for use in space technology in the development of spacecraft.

Known multi-purpose space platform for the creation of spacecraft (RU 2376212). The platform contains a frame made in the form of a parallelepiped, with side, top and bottom panels mounted on it, solar panels pivotally mounted on the frame. The intraframe space is divided by an intermediate panel located between the lower and upper panels and mounted on the frame, respectively, to the office system compartment and the payload compartment.

The disadvantage of this technical solution is the lack of the ability to place on the side walls (panels) of the hull some types of target equipment for spacecraft (antennas), which differ in significant dimensions, because the side walls of the platform are occupied by the frames of solar panels, and the placement of other payload elements on the side walls may prevent the opening of solar panels. In addition, the lack of a rotational drive for solar panels requires a constant change in the orientation of the spacecraft in order to ensure a constant orientation of the solar panels in the sun. This property limits the possibility of using the platform, in particular, it is not practical to use this space platform for spacecraft in geostationary orbit.

As the closest analogue (prototype), the well-known multi-purpose space platform for creating spacecraft (RU 2375267) was selected. The platform contains a service equipment module in the form of a rectangular parallelepiped formed by an end plate and four side boards. Inside, two intermediate chambers are installed, dividing the module into three compartments for office equipment. The instruments of the orientation and stabilization system and antennas are mounted on the side board. On one of the boards, docking nodes with a separation system are mounted. The propulsion system is mounted in the region of the proposed center of mass. Solar panels are mounted on brackets protruding beyond the module. The payload module installation nodes (MPN) are located on the free ends of the module side boards and protruding brackets. Moreover, the devices of the target payload equipment are located in the space between the solar panels and the free zone of the module from the side of its open part.

A number of significant disadvantages characteristic of the prototype is as follows:

1. The area occupied by the MPN is limited by the free space between the solar panels and the free zone of the module from the side of its open part, which imposes restrictions on the size of the MPN. With this arrangement, the conical part of the head fairing (GO) of the launch vehicle is not used;

2. The presence of separation of design functions into power and heat, i.e. use in the strength scheme mainly internal power elements to ensure rigidity, strength, geometric stability and thermoelasticity.

The task to which the invention is directed is to improve technical and operational characteristics, as well as reducing the time and cost of creating spacecraft (SC) with various target equipment on its basis.

The problem is solved in that the space platform containing a service system module (MSS) in the form of a rectangular parallelepiped, docking nodes with a separation system, a propulsion system, solar panels, has a spatial structure, and the structural and structural basis of the space platform is a cylindrical compartment (power structure of the hull ), made in the form of a mesh structure made of high-modulus carbon fiber reinforced plastic, with honeycomb panels fixed to it, interconnected by brackets, inside storage compartment, storage tanks for the working fluid for the propulsion system (DU) of the correction system (SC) and storage tanks for the working fluid for the DU of the orientation and stabilization system (SOS) are installed, the internal volume of the MCC housing, the top panel and the vertical panel are allocated for the placement of subsystem devices, in the composition of the multi-purpose space platform includes folding solar panels (SB), the solar battery drive is designed to orient the normal of the active surface of the SB panels in the sun, the propulsion system of the correction system and (SC) based on stationary xenon plasma engines mounted on titanium brackets, rod vectors of correction blocks passing through the actual center of mass of the spacecraft, to ensure the rod vectors through the actual center of mass, the correction blocks are mounted on titanium brackets with the ability to move in one plane and rotation around the axis, as the executive body to create control moments relative to the axes of the coordinate system associated with the spacecraft, the propulsion system of the system is used orientation and stabilization, motor orientation blocks are located on the radiator panels, in the area of contact with the upper panel and in the center of the power structure of the hull (CCM) from the side of the docking with the launch vehicle, at a distance from the center of mass of the spacecraft on the basis of the inventive platform, providing maximum shoulders control moments, the installation of spacecraft on the basis of this space platform on the launch vehicle during the implementation of group and associated launches is carried out using the separation device installed on the lower ground ngoutu CCM to provide temperature control equipment consisting of a platform exists thermal control system, the main application of the basic solutions are fully redundant fluid circuit CTP and passive control means.

The space platform is a structurally and functionally separate module that combines all the onboard service subsystems, which should provide the payload and provide all the necessary resources and services for it.

In the process of creating the spacecraft, the space platform is combined with the payload, which also represents a structurally and functionally separate module.

To provide easy integration with various payloads corresponding to different satellites, the space platform has simple and clearly defined unified interfaces, including:

- mechanical interface;

- electrical interface;

- thermal interface;

- information interface.

The construction and characteristics of the interfaces are universal and provide the ability to integrate various satellites with the payload platform, which correspond to the range of platform interface requirements.

All interfaces are spatially located in the docking areas of the platform structures and the payload and they are easily accessible at all stages of ground operation.

The space platform also provides for the installation of a satellite created on its basis on launch vehicles. For this purpose, it has a unified interface, consistent for all applicable means of output.

The interface with launch vehicles is also used for docking with ground transportation and technological equipment during the assembly, integration and testing of the platform and the satellite as a whole, as well as transportation and preparation at the launch site.

The space platform includes onboard systems capable of at least providing the following functions in ensuring the functioning of the spacecraft in the orbit, drift and installation at a given point of the geostationary orbit (GSO), the performance of targets during the life of:

- general management of all subsystems and equipment and interaction with the ground control complex;

- transferring the platform from the starting configuration to the working one;

- orientation and stabilization of the spacecraft hull with the required accuracy;

- spacecraft retention at a given GSO point with the required accuracy;

- the formation of control forces and moments in the process of orientation, stabilization of the spacecraft and control of its movement;

- power supply to all subsystems of the platform and MPN in all operating modes;

- maintaining the temperature conditions of all elements of the platform and MPN within the specified limits;

- maintaining all the elements of the spacecraft in the required mutual position at all stages of operation and protection from external influences;

- ensuring the conduct of ground testing and testing of the spacecraft and its on-board systems, interaction with ground-based testing equipment.

The inventive space platform is illustrated by drawings, which depict:

- figure 1 shows a General view (the operational state of the CP in axonometric projection);

- figure 2 shows a General view (the starting state of the KP in axonometric projection);

- figure 3 is a structural division of the platform;

- figure 4 - placement of storage tanks of the working fluid for propulsion systems.

The structural and structural basis of the platform is an unpressurized instrument compartment, which consists of the power structure of the housing 1, made in the form of a mesh structure of high-modulus carbon fiber and attached to it the instrument unit 2, made of three-layer honeycomb panels interconnected by brackets. The leaking unit 2 is used to accommodate the equipment of the service system module, made in the form of a rectangular parallelepiped from flat panels 3, 4, 5, 6, 7, 8, 9. The unit 2 is fixed to the end of the isogrid pipe 1. Panel 3 faces the outer surface to the solar panels 10, it has a rectangular shape with a round hole in the center in which the isogrid pipe 1 is placed. Panel 1 contains a part of the devices 11, electrical interfaces and hydraulic interfaces 12 for docking with the payload module. Along CCM 1 is a vertical panel 9, on which equipment 11 is located.

The internal volume of the MCC case, the top panel 3, the vertical panel 9 is allocated for the placement of devices of subsystems 11, rechargeable batteries 13, and elements 14 of the temperature control system. Also, part of the elements 14 of the STR is attached to the CCM 1.

Storage tanks for the working fluid 15 for the propulsion system of the correction system and storage tanks for the working fluid 16 for the remote control of the orientation and stabilization system are installed inside the cylindrical compartment of the CCM. The number of tanks may vary depending on the mission of the spacecraft built on the basis of this platform.

The multipurpose space platform includes folding solar panels 10. A solar battery drive 17 is designed to orient the normal of the active surface of the SB panels on the Sun.

The multipurpose space platform includes a propulsion system 18 of a correction system based on stationary xenon-mounted plasma engines placed on titanium brackets by rod vectors of correction blocks passing through the actual center of mass of the spacecraft. To ensure the passage of the thrust vectors through the actual center of mass, the correction units are mounted on titanium brackets with the possibility of movement in the same plane and rotation about the axis.

As the executive body for creating control moments relative to the axes of the coordinate system associated with the spacecraft, the propulsion system 19 of the orientation and stabilization system is used. The engine orientation blocks are located on the radiator panels, in the joint zone with the upper panel and in the center of the CCM from the side of the docking with the launch vehicle, at a distance from the spacecraft’s center of mass on the basis of the inventive platform, providing maximum control torque shoulders.

The installation of spacecraft on the basis of this space platform on the launch vehicle during the implementation of group and associated launches is carried out using the separation unit 20, installed on the lower frame of the CCM.

To ensure the temperature regime of the equipment, a thermal control system exists in the platform. The main basic solutions underlying the creation of the STR platform and the spacecraft based on the platform are the use of a combined subsystem based on heat pipes and a fully redundant liquid circuit (LC), supplemented by controlled electric heaters and passive regulation tools.

The adopted concept is based on the following principles:

1) As the main autonomous radiators 7 STR, the outer surface of the cellular dashboards of the platform is used, located along the “± Z” 5 axes and covered with the OCO-S thermoregulatory coating to ensure the removal of thermal power from the platform for a specified period of operation. Autonomous radiators 7 STR are used for thermoregulation of AB;

2) the LCD consists of two independent circuits (hydraulically not connected to each other): the main and backup and is designed to divert the heat flux from the equipment located on the platform to the radiators "± Z" PN, also the LCD can transfer excess heat flux between MCC radiator panels and payloads that will dock with this platform.

The area of radiation panels of the space platform is determined based on the necessary heat sink from the platform equipment.

To reduce unregulated heat transfer with the external environment, the design and equipment of the spacecraft are covered by thermal insulation.

In order to satisfy the requirements for the field of view of optical devices of the SOS, to minimize the design error of the alignment of the axes of these devices and the axes of the radiation patterns of the MPN antennas, as well as to constructively simplify the spacecraft, the optical SOS devices, cables connecting this equipment to other platform equipment are mounted on the payload module.

The inventive space platform in comparison with the prototype allows the following:

1. To increase the density of the layout created on the basis of the spacecraft platform due to a more complete use of the payload zone (SPG) of the launch vehicle. All the platform equipment is located in the lower part of the ZPG, the rest of the volume (including the conical part of the ZPG) remains under the MPN layout.

2. Reduce the spacecraft manufacturing time by using a recurrent space platform with simple and clearly defined unified interfaces and various MPN.

3. To reduce the cost of manufacturing spacecraft on the basis of this space platform, because there is no need to spend money on its completion and dequalification.

Claims (4)

1. A space platform containing a module of service systems (MSS) in the form of a rectangular parallelepiped, docking nodes with a separation system, a propulsion system, solar panels, characterized in that the space platform is a spatial structure, and the structural and power basis of the space platform is a cylindrical compartment (power structure of the case), made in the form of a mesh structure of high-modulus carbon fiber reinforced plastic, with honeycomb panels mounted on it, connected between battle with brackets, inside the cylindrical compartment, storage tanks for the working fluid for the propulsion system (DU) of the correction system (SC) and storage tanks of the working fluid for the DU of the orientation and stabilization system (SOS) are installed, the internal volume of the MCC housing, the top panel and the vertical panel are reserved for placement instruments of subsystems, the multipurpose space platform includes folding solar panels (SB), the solar battery drive is designed to orient the normal of the active surface of SB panels in the sun, installation of a correction system (SC) based on stationary xenon-mounted plasma engines mounted on titanium brackets by rod vectors of correction blocks passing through the actual center of mass of the spacecraft (SC) to ensure the passage of rod vectors through the actual center of mass correction blocks are mounted on titanium brackets with the possibility of movement in one plane and rotation about the axis, as an executive body for creating control moments relative to the axes of the system associated with the spacecraft we coordinate, the SOS propulsion system is used, the orientation motor blocks are located on the radiator panels, in the joint zone with the upper panel and in the center of the hull power structure from the side of the docking with the launch vehicle, at a distance from the SC center of mass on the basis of the claimed platform, providing maximum shoulders of control moments, the installation of spacecraft on the basis of this space platform on the launch vehicle during the implementation of group and associated launches is carried out using the separation device, installed on the lower frame of the CCM, to ensure the temperature of the equipment in the platform there is a temperature control system, the main basic solutions are the use of a fully redundant liquid circuit STR and passive regulation. 2. The space platform according to claim 1, characterized in that the number of tanks can vary depending on the mission of the spacecraft built on the basis of this platform. 3. The space platform according to claim 1, characterized in that the number of vertical panels can be more than one, if it is necessary to more fully use the layout space. 4. The space platform according to claim 1, characterized in that part of the propulsion system of the correction system is installed on the payload module.

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